公开(公告)号：US20240076999A1

公开(公告)日：2024-03-07

申请号：US18505408

申请日：2023-11-09

Applicant: RTX CORPORATION

Inventor： Frederick M. Schwarz ,  Nathan Snape

IPC: F01D25/08

CPC classification number: F01D25/08 ,  F05D2220/32 ,  F05D2240/60 ,  F05D2300/614

Abstract: A gas turbine engine includes a plurality of rotating components housed within a compressor section and a turbine section. A first tap is connected to the compressor section and configured to deliver air at a first pressure. A heat exchanger is connected downstream of the first tap. A flowpath is defined between a rotating surface and a non-rotating surface. The flowpath is connected downstream of the heat exchanger and is configured to deliver air to at least one of the plurality of rotating components. At least a portion of the non-rotating surface and the rotating surface includes a base metal. An insulation material is disposed on a surface along the flowpath.

公开(公告)号：US11920485B2

公开(公告)日：2024-03-05

申请号：US17887869

申请日：2022-08-15

Applicant: RTX Corporation

Inventor： Frederick M. Schwarz ,  Nathan Snape

IPC: F01D25/08

CPC classification number: F01D25/08 ,  F05D2220/32 ,  F05D2240/60 ,  F05D2300/614

Abstract: A gas turbine engine includes a plurality of rotating components housed within a compressor section and a turbine section. A first tap is connected to the compressor section and configured to deliver air at a first pressure. A heat exchanger is connected downstream of the first tap. A flowpath is defined between a rotating surface and a non-rotating surface. The flowpath is connected downstream of the heat exchanger and is configured to deliver air to at least one of the plurality of rotating components. At least a portion of the non-rotating surface and the rotating surface includes a base metal. An insulation material is disposed on a surface along the flowpath.

公开(公告)号：US11976863B2

公开(公告)日：2024-05-07

申请号：US17961606

申请日：2022-10-07

Applicant: RTX Corporation

Inventor： Nathan Snape ,  Joseph Brent Staubach

IPC: F25B9/00 ,  F02C3/04 ,  F02C7/18 ,  F02C7/22 ,  F02C7/224 ,  F25B9/06 ,  F25B40/02

CPC classification number: F25B9/008 ,  F02C3/04 ,  F02C7/185 ,  F02C7/222 ,  F02C7/224 ,  F25B9/004 ,  F25B9/06 ,  F25B40/02 ,  F25B2309/005 ,  F25B2309/061 ,  F25B2339/047 ,  F25B2400/14

Abstract: A gas turbine engine has a compressor section, a combustor, and a turbine section. An associated fluid is to be cooled and an associated fluid is to be heated. A transcritical vapor cycle heats the fluid to be heated, and cools the fluid to be cooled. The transcritical vapor cycle includes a gas cooler in which the fluid to be heated is heated by a refrigerant in the transcritical vapor cycle. An evaporator heat exchanger at which the fluid to be cooled is cooled by the refrigerant in the transcritical vapor cycle. A compressor upstream of the gas cooler compresses the refrigerant to a pressure above a critical point for the refrigerant. An expansion device expands the refrigerant downstream of the gas cooler, with the evaporator heat exchanger being downstream of the expansion device, and such that the refrigerant passing through the gas cooler to heat the fluid to be heated is generally above the critical point.